| 摘要 |
1,089,470. Fluid-pressure servomotor systems. DORNIER-WERKE G.m.b.H. Sept. 8, 1965 [Sept.18, 1964], No.38353/65. Heading G3P. A control surface of an aircraft is actuated by two servomotors 2, 3 Fig. 1 (not shown) connected in tandem and controlled by relay valves 7, 8 (Fig. 2) respectively, the spindles 13, 14 of the relay valves being interconnected by pivoted links 15, 16. Slidable on each of the spindles is a floating piston valve 36, the limits of sliding of the latter relative to the spindle being defined by stops 45, 46 on the spindle. Each relay valve is controlled by a polarized relay 30 receiving signals from an autopilot, the relay carrying a flapper 31 which co-operates with orifices 32, supplied from line 20 via restrictions 33, to vary the pressures in chambers 43, 44 of the relay valve, movement of the relay valve being fed back to the flapper via spring 34. Chambers 43, 44 are connected respectively to chambers 40, 39 at opposite ends of piston 36, these latter chambers containing springs 38 which urge the piston to a central position. When the relays 30 are energized, the respective relay valves 7, 8 are moved in opposite directions and the respective floating piston valves are moved in directions opposite to the directions of movement of the relay valves. If the power supply to one relay 30 should fail, the corresponding relay valve is moved by the movement of the other relay valve and causes the corresponding floating piston valve to move in the same direction as a result of chambers 43, 44 being connected to chambers 40, 39. Such movement of the floating piston valve vents a chamber 27 of a safety valve 26 thereby closing the latter to cut-off the fluid supply to the faulty electro-hydraulic relay 30.
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